EP2386726B1 - Channel wall section for a ring-shaped flow channel of an axial turbomaschine with blade tip gap adjustment, corresponding axial compressor and gas turbine - Google Patents

Channel wall section for a ring-shaped flow channel of an axial turbomaschine with blade tip gap adjustment, corresponding axial compressor and gas turbine Download PDF

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Publication number
EP2386726B1
EP2386726B1 EP10005053A EP10005053A EP2386726B1 EP 2386726 B1 EP2386726 B1 EP 2386726B1 EP 10005053 A EP10005053 A EP 10005053A EP 10005053 A EP10005053 A EP 10005053A EP 2386726 B1 EP2386726 B1 EP 2386726B1
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EP
European Patent Office
Prior art keywords
wall section
guide ring
ring
passage wall
axial
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
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EP10005053A
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German (de)
French (fr)
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EP2386726A1 (en
Inventor
Richard Graefe
Carsten Kaufmann
Rafael Labish
Marco Link
Oliver Dr. Schneider
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Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10005053A priority Critical patent/EP2386726B1/en
Priority to US13/104,186 priority patent/US8721270B2/en
Priority to JP2011106143A priority patent/JP5844068B2/en
Priority to CN201110122307.5A priority patent/CN102242644B/en
Publication of EP2386726A1 publication Critical patent/EP2386726A1/en
Application granted granted Critical
Publication of EP2386726B1 publication Critical patent/EP2386726B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Definitions

  • the invention relates to a channel wall portion of an annular flow channel of an axial turbomachine with radial gap adjustment.
  • flow channels are widely known.
  • the US 5,203,673 Such a device for regulating and adjusting radial gaps between the tips of the blades and the guide ring opposite thereto, which is part of the channel wall. It is provided that in the conical flow channel of the guide ring for adjusting radial gaps is axially displaceable.
  • three hydraulic cylinders are screwed in the guide vane support distributed over the circumference, the piston can move parallel to the machine axis of the turbine.
  • the conical gap between the flow path limiting wall surface of the guide ring and the correspondingly inclined tips of the blades can be adjusted by means of the axial displacement, the gap or the radial distance between the wall surface and blade tips.
  • the provision is made by means of coil springs, which move the guide ring back to its original position.
  • the use of a radial gap measuring system is provided with which the radial gap can be detected at one point.
  • the guide ring is then positioned axially in such a way that the smallest possible gap is achieved while avoiding the blade tip rubbing against the wall surface.
  • the disadvantage is the use of multiple hydraulic cylinders, since some of them may fail.
  • the object of the invention is to provide a compact duct wall portion for an annular flow channel of an axial turbomachine, with which a comparatively simple and reliable radial gap adjustment is possible without tilting of the guide ring takes place in case of failure of one of the hydraulic cylinder.
  • the guide ring which is arranged in a circumferential groove, has a first toothing on the front side, which rests against a second toothing arranged on a side wall of the circumferential groove, wherein it is additionally rotatable in the circumferential direction for the axial displacement of the displaceable guide ring.
  • the invention is based on the finding that the axial position of the guide ring is comparatively easily defined adjustable, when two mutually corresponding teeth always abut each other, of which a toothing is fixed and the other teeth relative to a toothing is slightly rotated, so that due to To the direction of displacement inclined tooth contact surfaces rotation of the teeth simultaneously causes or enforces their axial displacement.
  • the first toothing is intended to represent the rotatable toothing, which protrudes on the guide ring on the face side, ie from a plane perpendicular to the machine axis of the axial turbomachine.
  • the second toothing is fixed and arranged on the first toothing opposite side wall of the circumferential groove.
  • a plurality of uniformly distributed teeth over the circumference are provided, which means that at correspondingly many points the force is applied to adjust the guide ring, so that tilting of the guide ring can be safely avoided.
  • This also allows a distributed over the circumference uniform force application. Consequently, a local failure of the force introduction at only one point of the circumference can not occur. This results in a particularly reliable adjustability of the radial gaps, which are present between the flow path bounding inner wall surface of the guide ring and the tips of the passing below blades of the blades of the axial turbomachine.
  • the guide ring is by means of a spring element or a plurality of spring elements which are distributed over the circumference of the circumferential groove, always biased to the second toothing. An unwanted gap formation between the two gears can thus be safely avoided. This always leads to a clear axial position of the guide ring, which entails a clear gap.
  • spring elements are particularly disc springs.
  • the guide ring has an outwardly directed lateral surface with at least one external toothing, in the circumferentially distributed over the circumference of the channel wall portion, engage in these rotatably mounted gears, wherein an all gears encompassing collar is provided, the internal teeth with the gears engaged is.
  • the preferably uniformly distributed over the circumference gears can accordingly many positions take place the introduction of force to the rotation of the guide ring, which means that the external teeth, the gears and the internal teeth can be made relatively small.
  • This construction is space-saving and, moreover, inexpensive to produce.
  • Both the external toothing and the internal toothing need not be designed as an endless peripheral toothing on the adjusting ring or on the guide ring, since only a short Vermosweg of the guide ring for adjusting the radial gaps is required.
  • the outer teeth arranged on the outer lateral surface of the guide ring and / or the inner teeth arranged on the adjusting ring are provided only at those circumferential positions at which toothed wheels are also provided in the channel wall section.
  • the force is introduced into the adjusting ring preferably via hydraulically or electrically actuated, engaging it push rods, as they are already known from the prior art.
  • Such drive devices are also used for the adjustment of rotatable inlet guide vanes of axial compressors. They usually have only a single drive unit.
  • the flow channel may have two or more relevant axially and circumferentially movable guide rings which are jointly driven either by a respective adjusting ring or by a collar. If two guide rings of the one adjusting ring are jointly driven, a synchronous adjustment of the radial gaps of two blade rings can be done.
  • an abrasion layer or a honeycomb-shaped layer is preferably provided on the inwardly directed wall surface of the guide ring.
  • a simple mountability of the required for the rotation of the guide ring gears and collars is possible if an externally or internally arranged receptacle in the channel wall portion is provided for each gear, in which a shaft or hub of the gear is rotatable or storable. Since the outer ring surrounds all the gears, their shaft or hubs need not be particularly secured in the appropriate recordings. Consequently, the shafts or hubs can only be inserted into the receptacles without the need for further constructive elements for secure positioning. However, the use of such elements is not excluded.
  • the guide ring, the channel wall section and / or the adjusting ring or the adjusting rings are each in at least two segments, i. Guide ring segments, wall section segments or adjusting ring segments, divisible, which allows the half assembly of the construction.
  • the channel wall portion is used in an axial compressor of an axially flowed gas turbine.
  • the use of the proposed invention is of particular interest in particular when the radial gaps present in the turbine unit of the gas turbine can be adjusted by an axial displacement of the rotor. Since the flow channel of the turbine unit and the flow channel of the compressor of the gas turbine in principle have opposite conical inclinations, the displacement of the rotor in the turbine unit leads to a radial gap minimization and in the compressor to an opening of the radial column. With the proposed channel wall section, in particular, the enlargement of the compressor radial gaps described by the aforementioned effect can be compensated for and possibly overcompensated, which, despite the rotor displacement, improves the compressor efficiency and thus the efficiency of the gas turbine leads.
  • the proposed channel wall portion is particularly suitable for compressors, since they are often operated in a temperature range, which allows the use of the proposed construction particularly simple.
  • the single FIGURE shows a longitudinal section of a section of an annular flow channel 10.
  • the annular flow channel 10 extends concentrically along a machine axis 12 of the axial flow-through turbomachine.
  • the turbomachine shown here is designed as a compressor of a gas turbine.
  • the flow channel 10 comprises a wall section 14, which represents the radially outer boundary of the flow path. Radially inside the flow path is limited either by an inner wall 16 or by the lateral surface of the rotor 18.
  • blades 20 are provided in rings. Between the two illustrated blade rings is a vane ring with a number of distributed over the circumference vanes 22, which are each held on the channel wall portion 14 by means of a hammer-shaped attachment.
  • a guide ring 26 consisting of a plurality of segments is provided in an endless circumferential groove 24 in the wall section 14.
  • the guide ring 26 is located at the axial position of the rotor blade 20 shown on the left in FIG. 1.
  • the guide ring 26 has an inwardly directed wall surface 28.
  • the wall surface 28 limits the flow path and is the tips 30th the blades 28 under gap formation 32 opposite. The converging in this section wall surface 28 is therefore inclined relative to the machine axis 12 so that it is conical.
  • each receptacle 34 forms a pocket for a gear 38.
  • the gear 38 has a shaft or hub 40 which lies in the receptacle 34.
  • the gear 38 extends through the passage 36 and can engage in the arranged on the outer surface of the guide ring 26 outer teeth 35. All gears 38 are surrounded by a common adjusting ring 42, the internal teeth 44 with all gears 38 is engaged.
  • the outer teeth 35 has an axial width which is substantially greater than the axial width of the gear 38. This is necessary so that the guide ring 26 is always in spite of its displacement in the axial direction with the gears 38 in engagement.
  • the guide ring 26 is arranged in the endless circumferential groove 24.
  • a first toothing 50 is attached to the front side of the guide ring 26 by means of only schematically illustrated screws 48.
  • a second toothing 46 is fastened analogously.
  • the first toothing 50 and the second toothing 46 are in a toothing plane 52 to each other.
  • the toothing plane 52 is formed like a sawtooth. It can also be designed in the manner of a Hirth toothing, which supports the centering of the guide ring 26. However, the toothing plane 52 is not shown in longitudinal section, but rotated by 90 ° to - in the manner of a settlement. Both teeth 46, 50 thus extend in the circumferential direction and not - as shown - in the radial direction.
  • a push rod 45 is coupled on the adjusting ring 42.
  • retaining elements 47 provided with a Collars surround the collar 42.
  • the displacement of the guide ring 26 in the axial direction is effected by a rotation of the adjusting ring 42.
  • the rotation of the adjusting ring 42 is converted into a rotation of the gears 38, which transmit their rotation to the guide ring 26.
  • the adjacent teeth 46, 50 force due to their relative movement to each other then a displacement of the guide ring 26 in the axial direction, in FIG 1 to the left. This reduces the conical radial gaps 32.
  • an abrasive layer 56 is still provided on the wall surface 28 of the guide ring 26, which prevents damage in the case of a brushing of the blade tips 30 on the guide ring 26.
  • the holding elements 47 are adapted accordingly.
  • the adjusting ring 42 is then designed rather as a drum.
  • the adjustment of the size of the radial gaps between the wall surface 28 of the guide ring 26 and the opposite ends 30 of the blades 20 can already be performed during startup or during operation of the turbomachine or the gas turbine.
  • the radial gap adjustment can also take place as a function of a measured, actual radial gap.
  • gears 38 and the teeth 46, 50 may possibly be dispensed with lubricant, which is easy to maintain. Possibly. the sliding surfaces of the teeth 46, 50 are coated with polytetrafluoroethylene (PTFE). This allows a low-loss relative movement of the two gears 46, 50th
  • the invention provides a channel wall portion 14 of an annular flow channel 10 of an axial turbomachine which provides a particular simple, compact mechanism for adjusting radial gaps 32 between the inner wall surface 28 of a guide ring 26 and the blade edge 30 opposite this wall surface 28.
  • the guide ring 26 has frontally a first toothing 50 which rests on a on the side wall 27 of the guide ring 26 receiving circumferential groove 24 arranged second toothing 46, wherein the axial displacement of the displaceable guide ring 26 thereof is rotatable in the circumferential direction.

Description

Die Erfindung betrifft einen Kanalwandabschnitt eines ringförmigen Strömungskanals einer Axialturbomaschine mit Radialspalteinstellung. Derartige Strömungskanäle sind vielfach bekannt. Beispielsweise offenbart die US 5,203,673 eine derartige Vorrichtung zum Regeln und Einstellen von Radialspalten zwischen den Spitzen der Laufschaufeln und des diesen gegenüberliegenden Führungsrings, welcher Teil der Kanalwand ist. Dabei ist vorgesehen, dass im konischen Strömungskanal der Führungsring zur Einstellung von Radialspalten axial verschiebbar ist. Zur axialen Verschiebung des Führungsrings sind im Leitschaufelträger über den Umfang verteilt drei hydraulische Zylinder eingeschraubt, deren Kolben sich parallel zur Maschinenachse der Turbine bewegen können. In Verbindung mit dem konischen Spalt zwischen der den Strömungspfad begrenzenden Wandfläche des Führungsrings und den dazu entsprechend geneigten Spitzen der Laufschaufeln kann mit Hilfe der Axialverschiebung das Spaltmaß bzw. der radiale Abstand zwischen Wandfläche und Schaufelspitzen eingestellt werden. Die Rückstellung erfolgt mit Hilfe von Schraubenfedern, die den Führungsring in die ursprüngliche Position zurückbewegen. Gleichzeitig ist die Verwendung eines Radialspalt-Messsystems vorgesehen, mit dem an einer Stelle der Radialspalt erfasst werden kann. In Abhängigkeit vom erfassten Spaltmaß wird dann der Führungsring axial so positioniert, dass unter Vermeidung von Anstreifen der Schaufelspitze an der Wandfläche ein möglichst kleines Spaltmaß erzielt wird. Nachteilig ist jedoch die Verwendung mehrerer hydraulischer Zylinder, da einzelne davon ausfallen können. Dies würde im Verstellfall zu einem Verkanten des Führungsrings führen. Ein weiterer Nachteil der Vorrichtung ist die an nur drei Stellen vorgesehene, eher punktuelle Einleitung der zur Axialverschiebung des Führungsrings erforderlichen Verstellkraft mit Hilfe der hydraulischen Zylinder. Jeder Zylinder muss somit einen vergleichsweise großen Anteil der Gesamtverstellkraft übertragen können, was raumgreifende Zylinder erforderlich macht.The invention relates to a channel wall portion of an annular flow channel of an axial turbomachine with radial gap adjustment. Such flow channels are widely known. For example, the US 5,203,673 Such a device for regulating and adjusting radial gaps between the tips of the blades and the guide ring opposite thereto, which is part of the channel wall. It is provided that in the conical flow channel of the guide ring for adjusting radial gaps is axially displaceable. For axial displacement of the guide ring three hydraulic cylinders are screwed in the guide vane support distributed over the circumference, the piston can move parallel to the machine axis of the turbine. In conjunction with the conical gap between the flow path limiting wall surface of the guide ring and the correspondingly inclined tips of the blades can be adjusted by means of the axial displacement, the gap or the radial distance between the wall surface and blade tips. The provision is made by means of coil springs, which move the guide ring back to its original position. At the same time, the use of a radial gap measuring system is provided with which the radial gap can be detected at one point. Depending on the detected gap dimension, the guide ring is then positioned axially in such a way that the smallest possible gap is achieved while avoiding the blade tip rubbing against the wall surface. However, the disadvantage is the use of multiple hydraulic cylinders, since some of them may fail. This would lead to tilting of the guide ring in the case of adjustment. Another disadvantage of the device is provided at only three places, rather punctual introduction of the required axial displacement of the guide ring adjustment by means of hydraulic cylinder. Each cylinder must therefore be able to transmit a comparatively large proportion of Gesamtverstellkraft, which makes bulky cylinder is required.

Aufgabe der Erfindung ist die Bereitstellung eines kompakten Kanalwandabschnitts für einen ringförmigen Strömungskanal einer Axialturbomaschine, mit welchem eine vergleichsweise einfache und zuverlässige Radialspalteinstellung möglich ist, ohne das ein Verkanten des Führungsrings beim Ausfall eines der hydraulischen Zylinder erfolgt.The object of the invention is to provide a compact duct wall portion for an annular flow channel of an axial turbomachine, with which a comparatively simple and reliable radial gap adjustment is possible without tilting of the guide ring takes place in case of failure of one of the hydraulic cylinder.

Die der Erfindung zugrunde liegende Aufgabe wird mit einem Kanalwandabschnitt gemäß den Merkmalen des Anspruchs 1 gelöst, dessen Oberbegriff in US 3 227 418 offenbart wird.The object underlying the invention is achieved with a channel wall section according to the features of claim 1, the preamble in US 3,227,418 is disclosed.

Erfindungsgemäß ist vorgesehen, dass der in eine Umfangsnut angeordnete Führungsring stirnseitig eine erste Verzahnung aufweist, welche an einer an einer Seitenwand der Umfangsnut angeordneten zweiten Verzahnung anliegt, wobei zur Axialverschiebung des verschiebbaren Führungsrings dieser zusätzlich in Umfangsrichtung drehbar ist. Der Erfindung liegt die Erkenntnis zugrunde, dass die axiale Position des Führungsrings vergleichsweise einfach definiert einstellbar ist, wenn zwei zueinander korrespondierende Verzahnungen stets aneinander anliegen, von denen eine Verzahnung feststehend ist und die andere Verzahnung gegenüber der einen Verzahnung geringfügig verdrehbar ist, so dass aufgrund der zur Verschieberichtung geneigten Zahnkontaktflächen eine Drehung der Verzahnung gleichzeitig deren axiale Verschiebung bewirkt bzw. erzwingt. Gemäß der Erfindung soll die erste Verzahnung die drehbare Verzahnung darstellen, welche am Führungsring stirnseitig, d.h. aus einer Ebene senkrecht zur Maschinenachse der Axialturbomaschine, ausragt. Die zweite Verzahnung ist feststehend und an der der ersten Verzahnung gegenüber liegenden Seitenwand der Umfangsnut angeordnet. Üblicherweise sind jeweils eine Vielzahl von über dem Umfang gleichverteilten Zähnen vorgesehen, was dazu führt, dass an entsprechend vielen Stellen die Krafteinleitung zur Verstellung des Führungsrings erfolgt, so dass ein Verkanten des Führungsrings sicher vermieden werden kann. Dies ermöglicht außerdem eine - über den Umfang verteilt - gleichmäßige Krafteinleitung. Ein lokaler Ausfall der Krafteinleitung an nur einer Stelle des Umfangs kann folglich nicht auftreten. Dies führt zu einer besonders zuverlässigen Einstellbarkeit der Radialspalte, welche zwischen der den Strömungsweg begrenzenden inneren Wandfläche des Führungsrings und den Spitzen der darunter vorbeilaufenden Schaufelblättern der Laufschaufeln der Axialturbomaschine vorhanden sind.According to the invention, the guide ring, which is arranged in a circumferential groove, has a first toothing on the front side, which rests against a second toothing arranged on a side wall of the circumferential groove, wherein it is additionally rotatable in the circumferential direction for the axial displacement of the displaceable guide ring. The invention is based on the finding that the axial position of the guide ring is comparatively easily defined adjustable, when two mutually corresponding teeth always abut each other, of which a toothing is fixed and the other teeth relative to a toothing is slightly rotated, so that due to To the direction of displacement inclined tooth contact surfaces rotation of the teeth simultaneously causes or enforces their axial displacement. According to the invention, the first toothing is intended to represent the rotatable toothing, which protrudes on the guide ring on the face side, ie from a plane perpendicular to the machine axis of the axial turbomachine. The second toothing is fixed and arranged on the first toothing opposite side wall of the circumferential groove. Usually, a plurality of uniformly distributed teeth over the circumference are provided, which means that at correspondingly many points the force is applied to adjust the guide ring, so that tilting of the guide ring can be safely avoided. This also allows a distributed over the circumference uniform force application. Consequently, a local failure of the force introduction at only one point of the circumference can not occur. This results in a particularly reliable adjustability of the radial gaps, which are present between the flow path bounding inner wall surface of the guide ring and the tips of the passing below blades of the blades of the axial turbomachine.

Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

Gemäß einer ersten vorteilhaften Ausgestaltung liegt der Führungsring mittels eines Federelementes oder mehrerer Federelemente, die über den Umfang der Umfangsnut verteilt sind, stets vorgespannt an der zweiten Verzahnung an. Eine ungewollte Spaltbildung zwischen den beiden Verzahnungen kann somit sicher vermieden werden. Dies führt stets zu einer eindeutigen axialen Position des Führungsrings, was ein eindeutiges Spaltmaß nach sich zieht. Als Federelemente eignen sich besonders Tellerfedern.According to a first advantageous embodiment of the guide ring is by means of a spring element or a plurality of spring elements which are distributed over the circumference of the circumferential groove, always biased to the second toothing. An unwanted gap formation between the two gears can thus be safely avoided. This always leads to a clear axial position of the guide ring, which entails a clear gap. As spring elements are particularly disc springs.

Nach einer weiteren vorteilhaften Ausgestaltung weist der Führungsring eine nach außen gerichtete Mantelfläche mit zumindest einer Außenverzahnung auf, in die über den Umfang des Kanalwandabschnitts verteilte, in diesen drehgelagerte Zahnräder eingreifen, wobei ein alle Zahnräder umgreifender Stellring vorgesehen ist, dessen Innenverzahnung mit den Zahnrädern im Eingriff ist. Damit kann eine besonders einfache Konstruktion angegeben werden, mit welcher der Führungsring in Umfangsrichtung verdrehbar bzw. schwenkbar ist. Zudem wird der Führungsring radial mit Hilfe der Zahnräder und des Stellrings abgestützt und getragen. Gleichzeitig kann damit die Zentrierung des Stellrings und des Führungsrings eingestellt werden. Weiter noch, mit Hilfe der über den Umfang vorzugsweise gleichmäßig verteilten Zahnrädern kann an entsprechend vielen Positionen die Krafteinleitung zur Verdrehung des Führungsrings erfolgen, was dazu führt, dass die Außenverzahnung, die Zahnräder und die Innenverzahnung vergleichsweise klein ausgebildet sein können. Diese Konstruktion ist platzsparend und darüber hinaus kostengünstig herstellbar. Sowohl die Außenverzahnung und die Innenverzahnung müssen nicht als endlos umlaufende Verzahnung am Stellring bzw. am Führungsring ausgebildet sein, da lediglich ein kurzer Verdrehweg des Führungsrings zur Einstellung der Radialspalte erforderlich ist. Dementsprechend sind die an der äußeren Mantelfläche des Führungsrings angeordnete Außenverzahnung und/oder die am Stellring angeordnete Innenverzahnung nur an denjenigen Umfangspositionen vorgesehen, an denen auch Zahnräder im Kanalwandabschnitt vorgesehen sind.According to a further advantageous embodiment, the guide ring has an outwardly directed lateral surface with at least one external toothing, in the circumferentially distributed over the circumference of the channel wall portion, engage in these rotatably mounted gears, wherein an all gears encompassing collar is provided, the internal teeth with the gears engaged is. Thus, a particularly simple construction can be specified, with which the guide ring is rotatable or pivotable in the circumferential direction. In addition, the guide ring is supported and supported radially by means of the gears and the adjusting ring. At the same time so that the centering of the adjusting ring and the guide ring can be adjusted. Still further, with the aid of the preferably uniformly distributed over the circumference gears can accordingly many positions take place the introduction of force to the rotation of the guide ring, which means that the external teeth, the gears and the internal teeth can be made relatively small. This construction is space-saving and, moreover, inexpensive to produce. Both the external toothing and the internal toothing need not be designed as an endless peripheral toothing on the adjusting ring or on the guide ring, since only a short Verdrehweg of the guide ring for adjusting the radial gaps is required. Accordingly, the outer teeth arranged on the outer lateral surface of the guide ring and / or the inner teeth arranged on the adjusting ring are provided only at those circumferential positions at which toothed wheels are also provided in the channel wall section.

Die Krafteinleitung in den Stellring erfolgt vorzugsweise über hydraulisch oder elektrisch betätigte, daran angreifende Schubstangen, wie sie aus dem Stand der Technik bereits bekannt sind. Derartige Antriebsvorrichtungen werden auch eingesetzt zur Verstellung von verdrehbaren Einlassleitschaufeln von Axialverdichtern. Sie weisen meist nur eine einzige Antriebseinheit auf.The force is introduced into the adjusting ring preferably via hydraulically or electrically actuated, engaging it push rods, as they are already known from the prior art. Such drive devices are also used for the adjustment of rotatable inlet guide vanes of axial compressors. They usually have only a single drive unit.

Gemäß einer weiteren vorteilhaften Ausgestaltung kann der Strömungskanal zwei oder mehr betreffende axial und in Umfangsrichtung bewegliche Führungsringe aufweisen, die entweder von je einem Stellring oder auch von dem einen Stellring gemeinschaftlich antreibbar sind. Sofern zwei Führungsringe von dem einen Stellring gemeinschaftlich antreibbar sind, kann eine synchrone Verstellung der Radialspalte zweier Laufschaufelkränze erfolgen.According to a further advantageous embodiment, the flow channel may have two or more relevant axially and circumferentially movable guide rings which are jointly driven either by a respective adjusting ring or by a collar. If two guide rings of the one adjusting ring are jointly driven, a synchronous adjustment of the radial gaps of two blade rings can be done.

Um eine Schädigung der Spitzen der Schaufelblätter von Laufschaufeln bei ungewolltem Kontakt mit der Wandfläche des Führungsrings zu vermeiden, ist vorzugsweise die Verwendung einer Abrasionsschicht oder einer honigwabenförmigen Schicht an der nach innen gerichteten Wandfläche des Führungsrings vorgesehen.In order to avoid damaging the tips of the blades of blades on accidental contact with the wall surface of the guide ring, the use of an abrasion layer or a honeycomb-shaped layer is preferably provided on the inwardly directed wall surface of the guide ring.

Eine einfache Montierbarkeit der zur Verdrehung des Führungsrings erforderlichen Zahnräder und Stellringe ist möglich, wenn für jedes Zahnrad eine außenseitig oder innenseitig angeordnete Aufnahme im Kanalwandabschnitt vorgesehen ist, in welcher eine Welle oder Nabe des Zahnrads drehlagerbar bzw. lagerbar ist. Da der Außenring alle Zahnräder umgreift, müssen deren Welle bzw. Naben nicht besonders in den dafür vorgesehenen Aufnahmen gesichert werden. Folglich können die Wellen oder Naben in die Aufnahmen lediglich eingelegt sein, ohne dass weitere konstruktive Elemente zur sicheren Positionierung erforderlich sind. Die Verwendung derartiger Elemente ist jedoch nicht ausgeschlossen.A simple mountability of the required for the rotation of the guide ring gears and collars is possible if an externally or internally arranged receptacle in the channel wall portion is provided for each gear, in which a shaft or hub of the gear is rotatable or storable. Since the outer ring surrounds all the gears, their shaft or hubs need not be particularly secured in the appropriate recordings. Consequently, the shafts or hubs can only be inserted into the receptacles without the need for further constructive elements for secure positioning. However, the use of such elements is not excluded.

Um den vorgeschlagenen Kanalwandabschnitt auch in stationär betriebenen, hälftig teilbaren Axialturbomaschinen nutzen zu können, sind der Führungsring, der Kanalwandabschnitt und/oder der Stellring oder die Stellringe jeweils in mindestens zwei Segmente, d.h. Führungsringsegmente, Wandabschnittsegmente bzw. Stellringsegmente, teilbar, was den hälftigen Zusammenbau der Konstruktion ermöglicht. Vorzugweise wird der Kanalwandabschnitt in einem Axialverdichter einer axial durchströmten Gasturbine verwendet.In order to be able to use the proposed channel wall section also in stationary, half-divisible axial turbomachines, the guide ring, the channel wall section and / or the adjusting ring or the adjusting rings are each in at least two segments, i. Guide ring segments, wall section segments or adjusting ring segments, divisible, which allows the half assembly of the construction. Preferably, the channel wall portion is used in an axial compressor of an axially flowed gas turbine.

Der Einsatz der vorgeschlagenen Erfindung ist insbesondere dann von besonderem Interesse, wenn die in der Turbineneinheit der Gasturbine vorhandenen Radialspalte durch eine Axialverschiebung des Rotors einstellbar sind. Da der Strömungskanal der Turbineneinheit und der Strömungskanal des Verdichters der Gasturbine prinzipiell gegensätzliche konische Neigungen aufweisen, führt die Verschiebung des Rotors in der Turbineneinheit zu einer Radialspaltminimierung und im Verdichter zu einer Öffnung der Radialspalte. Mit dem vorgeschlagenen Kanalwandabschnitt kann insbesondere die durch vorgenannten Effekt beschriebene Vergrößerung der Verdichter-Radialspalte kompensiert und ggf. überkompensiert werden, was trotz der Rotorverschiebung zu einer Verbesserung des Verdichterwirkungsgrades und somit der Effizienz der Gasturbine führt. Der vorgeschlagene Kanalwandabschnitt eignet sich insbesondere für Verdichter, da diese häufig in einem Temperaturbereich betrieben werden, welche den Einsatz der vorgeschlagenen Konstruktion besonders einfach ermöglicht.The use of the proposed invention is of particular interest in particular when the radial gaps present in the turbine unit of the gas turbine can be adjusted by an axial displacement of the rotor. Since the flow channel of the turbine unit and the flow channel of the compressor of the gas turbine in principle have opposite conical inclinations, the displacement of the rotor in the turbine unit leads to a radial gap minimization and in the compressor to an opening of the radial column. With the proposed channel wall section, in particular, the enlargement of the compressor radial gaps described by the aforementioned effect can be compensated for and possibly overcompensated, which, despite the rotor displacement, improves the compressor efficiency and thus the efficiency of the gas turbine leads. The proposed channel wall portion is particularly suitable for compressors, since they are often operated in a temperature range, which allows the use of the proposed construction particularly simple.

Die voranbeschriebene Erfindung wird nachfolgend anhand einer einzigen Längsschnittdarstellung näher erläutert. Die Zeichnung zeigt:

FIG 1
einen Längsschnitt durch einen Ausschnitt eines ringförmigen Strömungskanals einer Axialturbomaschine.
The above-described invention will be explained in more detail with reference to a single longitudinal section. The drawing shows:
FIG. 1
a longitudinal section through a section of an annular flow channel of an axial turbomachine.

Die einzige Figur zeigt in einem Längsschnitt einen Ausschnitt eines ringförmigen Strömungskanals 10. Der ringförmige Strömungskanal 10 erstreckt sich konzentrisch entlang einer Maschinenachse 12 der axial durchströmten Turbomaschine. Die hier dargestellte Turbomaschine ist als Verdichter einer Gasturbine ausgestaltet. Der Strömungskanal 10 umfasst einen Wandabschnitt 14, welcher die radial äußere Begrenzung des Strömungswegs darstellt. Radial innen wird der Strömungsweg entweder von einer inneren Wand 16 oder von der Mantelfläche des Rotors 18 begrenzt. An unterschiedlichen axialen Positionen des Rotors 18 sind Laufschaufeln 20 in Kränzen vorgesehen. Zwischen den beiden dargestellten Laufschaufelkränzen befindet sich ein Leitschaufelkranz mit einer Anzahl von über den Umfang verteilten Leitschaufeln 22, welche jeweils am Kanalwandabschnitt 14 mit Hilfe einer hammerförmigen Befestigung gehalten sind.The single FIGURE shows a longitudinal section of a section of an annular flow channel 10. The annular flow channel 10 extends concentrically along a machine axis 12 of the axial flow-through turbomachine. The turbomachine shown here is designed as a compressor of a gas turbine. The flow channel 10 comprises a wall section 14, which represents the radially outer boundary of the flow path. Radially inside the flow path is limited either by an inner wall 16 or by the lateral surface of the rotor 18. At different axial positions of the rotor 18 blades 20 are provided in rings. Between the two illustrated blade rings is a vane ring with a number of distributed over the circumference vanes 22, which are each held on the channel wall portion 14 by means of a hammer-shaped attachment.

Stromauf des in FIG 1 von links nach rechts durchströmten Strömungskanals 10 des Verdichters ist ein aus mehreren Segmenten bestehender Führungsring 26 in einer endlos im Wandabschnitt 14 umlaufenden Umfangsnut 24 vorgesehen. Der Führungsring 26 befindet sich an der axialen Position der in FIG 1 links dargestellten Laufschaufel 20. Der Führungsring 26 weist eine nach innen gerichtete Wandfläche 28 auf. Die Wandfläche 28 begrenzt den Strömungsweg und liegt den Spitzen 30 der Laufschaufeln 28 unter Spaltbildung 32 gegenüber. Die in diesem Abschnitt konvergente Wandfläche 28 ist demnach gegenüber der Maschinenachse 12 geneigt, so dass sie konisch ausgebildet ist.Upstream of the flow channel 10 of the compressor, which flows through from left to right in FIG. 1, a guide ring 26 consisting of a plurality of segments is provided in an endless circumferential groove 24 in the wall section 14. The guide ring 26 is located at the axial position of the rotor blade 20 shown on the left in FIG. 1. The guide ring 26 has an inwardly directed wall surface 28. The wall surface 28 limits the flow path and is the tips 30th the blades 28 under gap formation 32 opposite. The converging in this section wall surface 28 is therefore inclined relative to the machine axis 12 so that it is conical.

Über den Umfang des Kanalwandabschnitts 14 sind radial außerhalb des Führungsrings 26 paarweise mehrere Aufnahmen 34 und Durchgänge 36 verteilt. Jede Aufnahme 34 bildet eine Tasche für ein Zahnrad 38. Das Zahnrad 38 weist eine Welle oder Nabe 40 auf, welche in der Aufnahme 34 liegt. Das Zahnrad 38 durchragt den Durchgang 36 und kann in die an der äußeren Fläche des Führungsrings 26 angeordnete Außenverzahnung 35 eingreifen. Alle Zahnräder 38 sind von einem gemeinsamen Stellring 42 umgeben, dessen Innenverzahnung 44 mit allen Zahnrädern 38 in Eingriff steht. Die Außenverzahnung 35 weist eine axial Breite auf, die wesentlich größer ist als die axiale Breite des Zahnrades 38. Dies ist erforderlich, damit der Führungsring 26 trotz seiner Verschiebung in Axialrichtung stets mit den Zahnrädern 38 in Eingriff ist.Over the circumference of the channel wall portion 14 a plurality of receptacles 34 and passages 36 are distributed radially outside the guide ring 26 in pairs. Each receptacle 34 forms a pocket for a gear 38. The gear 38 has a shaft or hub 40 which lies in the receptacle 34. The gear 38 extends through the passage 36 and can engage in the arranged on the outer surface of the guide ring 26 outer teeth 35. All gears 38 are surrounded by a common adjusting ring 42, the internal teeth 44 with all gears 38 is engaged. The outer teeth 35 has an axial width which is substantially greater than the axial width of the gear 38. This is necessary so that the guide ring 26 is always in spite of its displacement in the axial direction with the gears 38 in engagement.

Der Führungsring 26 ist in der endlosen Umfangsnut 24 angeordnet. Eine erste Verzahnung 50 ist stirnseitig am Führungsring 26 mit Hilfe nur schematisch dargestellter Schrauben 48 befestigt. An der in FIG 1 rechts dargestellten Seitenwand 27 der Umfangsnut 24 ist eine zweite Verzahnung 46 analog befestigt. Die erste Verzahnung 50 und die zweite Verzahnung 46 liegen in einer Verzahnungsebene 52 aneinander. Die Verzahnungsebene 52 ist sägezahnförmig ausgebildet. Sie kann auch nach Art einer Hirth-Verzahnung ausgebildet sein, welche die Zentrierung des Führungsrings 26 unterstützt. Die Verzahnungsebene 52 ist jedoch nicht im Längsschnitt dargestellt, sondern um 90° dazu verdreht - nach Art einer Abwicklung. Beide Verzahnungen 46, 50 erstrecken sich somit in Umfangsrichtung und nicht - wie dargestellt - in Radialrichtung.The guide ring 26 is arranged in the endless circumferential groove 24. A first toothing 50 is attached to the front side of the guide ring 26 by means of only schematically illustrated screws 48. At the side wall 27 of the circumferential groove 24 shown on the right in FIG. 1, a second toothing 46 is fastened analogously. The first toothing 50 and the second toothing 46 are in a toothing plane 52 to each other. The toothing plane 52 is formed like a sawtooth. It can also be designed in the manner of a Hirth toothing, which supports the centering of the guide ring 26. However, the toothing plane 52 is not shown in longitudinal section, but rotated by 90 ° to - in the manner of a settlement. Both teeth 46, 50 thus extend in the circumferential direction and not - as shown - in the radial direction.

An dem Stellring 42 ist eine Schubstange 45 angekoppelt. Zur axialen und radialen Führung des Stellrings 42 sind seitlich dazu angeordnete Halteelemente 47 vorgesehen, die mit einem Kragen den Stellring 42 umgreifen. Die Verschiebung des Führungsrings 26 in Axialrichtung erfolgt durch eine Verdrehung des Stellrings 42. Mit Hilfe der Innenverzahnung 44 wird die Drehung des Stellrings 42 in eine Drehung der Zahnräder 38 umgesetzt, die ihre Drehung auf den Führungsring 26 übertragen. Die aneinander liegenden Verzahnungen 46, 50 erzwingen aufgrund Ihrer Relativbewegung zueinander dann eine Verschiebung des Führungsrings 26 in Axialrichtung, in FIG 1 nach links. Hierdurch verkleinern sich die konischen Radialspalte 32. Das axiale Zurückbewegen des Führungsrings 26 erfolgt mit Hilfe einer entgegengesetzten Drehung des Stellrings 42 in Verbindung mit den über den Umfang verteilten Federelementen 54, die zwischen der anderen Seitenwand der Umfangsnut 24 und dem Führungsring 26 angeordnet sind und letztgenannten stets an die zweite Verzahnung 46 pressen.On the adjusting ring 42, a push rod 45 is coupled. For axial and radial guidance of the adjusting ring 42 are arranged laterally thereto retaining elements 47 provided with a Collars surround the collar 42. The displacement of the guide ring 26 in the axial direction is effected by a rotation of the adjusting ring 42. With the aid of the internal teeth 44, the rotation of the adjusting ring 42 is converted into a rotation of the gears 38, which transmit their rotation to the guide ring 26. The adjacent teeth 46, 50 force due to their relative movement to each other then a displacement of the guide ring 26 in the axial direction, in FIG 1 to the left. This reduces the conical radial gaps 32. The axial movement back of the guide ring 26 by means of an opposite rotation of the adjusting ring 42 in conjunction with the distributed over the circumference spring elements 54 which are disposed between the other side wall of the circumferential groove 24 and the guide ring 26 and the latter always press on the second toothing 46.

Daneben ist noch eine abrasive Schicht 56 an der Wandfläche 28 des Führungsrings 26 vorgesehen, welche im Falle eines Anstreifens der Schaufelspitzen 30 am Führungsring 26 einen Schaden verhindert.In addition, an abrasive layer 56 is still provided on the wall surface 28 of the guide ring 26, which prevents damage in the case of a brushing of the blade tips 30 on the guide ring 26.

Für den Fall, dass der Einstellring 24 gemeinschaftlich zwei Führungsringe 26 antreiben soll, sind die Halteelemente 47 dementsprechend angepasst. Der Stellring 42 ist dann eher als Trommel ausgebildet. Selbstverständlich ist es möglich, die Radialspalteinstellung synchron oder unabhängig von einer axialen Rotorverschiebung der Gasturbine durchzuführen.In the event that the adjusting ring 24 is to jointly drive two guide rings 26, the holding elements 47 are adapted accordingly. The adjusting ring 42 is then designed rather as a drum. Of course, it is possible to perform the radial gap adjustment synchronously or independently of an axial rotor displacement of the gas turbine.

Die Einstellung der Größe der Radialspalte zwischen der Wandfläche 28 des Führungsrings 26 und den dieser gegenüber liegenden Spitzen 30 der Schaufeln 20 kann bereits während der Inbetriebnahme oder auch während des Betriebs der Turbomaschine bzw. der Gasturbine ausgeführt werden. Ergänzend oder alternativ kann die Radialspalteinstellung auch in Abhängigkeit eines gemessenen, tatsächlichen Radialspalts erfolgen. Durch die Verkleinerung der Radialspalte 32 werden die Radialspalt-Verluste reduziert, was zu einer erhöhten Energieumsetzung im Verdichter führt.The adjustment of the size of the radial gaps between the wall surface 28 of the guide ring 26 and the opposite ends 30 of the blades 20 can already be performed during startup or during operation of the turbomachine or the gas turbine. In addition or as an alternative, the radial gap adjustment can also take place as a function of a measured, actual radial gap. By reducing the radial gap 32, the radial gap losses are reduced, which leads to an increased energy conversion in the compressor.

Durch die Verwendung geeigneter Werkstoffe für die Zahnräder 38 und der Verzahnungen 46, 50 kann ggf. auf Schmiermittel verzichtet werden, was wartungsfreundlich ist. Ggf. sind die Gleitflächen der Verzahnungen 46, 50 mit Polytetrafluorethen (PTFE) beschichtet. Dies ermöglicht eine verlustarme Relativbewegung der beiden Verzahnungen 46, 50.By using suitable materials for the gears 38 and the teeth 46, 50 may possibly be dispensed with lubricant, which is easy to maintain. Possibly. the sliding surfaces of the teeth 46, 50 are coated with polytetrafluoroethylene (PTFE). This allows a low-loss relative movement of the two gears 46, 50th

Insgesamt wird mit der Erfindung ein Kanalwandabschnitt 14 eines ringförmigen Strömungskanals 10 einer axialen Turbomaschine angegeben, der einen besonderen einfachen, kompakten Mechanismus zur Einstellung von Radialspalten 32 zwischen der inneren Wandfläche 28 eines Führungsrings 26 und den dieser Wandfläche 28 gegenüber liegenden Laufschaufelblattspitzen 30 angibt. Erfindungsgemäß ist dazu vorgesehen, dass der Führungsring 26 stirnseitig eine erste Verzahnung 50 aufweist, welche an einer an der Seitenwand 27 der den Führungsring 26 aufnehmenden Umfangsnut 24 angeordneten zweiten Verzahnung 46 anliegt, wobei zur Axialverschiebung des verschiebbaren Führungsrings 26 dieser in Umfangsrichtung drehbar ist.Overall, the invention provides a channel wall portion 14 of an annular flow channel 10 of an axial turbomachine which provides a particular simple, compact mechanism for adjusting radial gaps 32 between the inner wall surface 28 of a guide ring 26 and the blade edge 30 opposite this wall surface 28. According to the invention it is provided that the guide ring 26 has frontally a first toothing 50 which rests on a on the side wall 27 of the guide ring 26 receiving circumferential groove 24 arranged second toothing 46, wherein the axial displacement of the displaceable guide ring 26 thereof is rotatable in the circumferential direction.

Claims (12)

  1. Passage wall section (14) for an annular flow passage (10) of an axial turbomachine,
    in the inwardly pointing surface of which provision is made for an encompassing circumferential groove (24), and
    with a guide ring (26) which is arranged in the circumferential groove (24), delimits the flow passage (10), and for adjusting radial gaps (32) which exist in each case between a wall surface (28) of the guide ring (26) and the rotor blade airfoil tips (30) lying opposite the wall surface (28), is displaceable at least in the axial direction, wherein for axial displacement of the displaceable guide ring (26) this is rotatable in the circumferential direction,
    characterized in that
    the guide ring (26), on the end face, comprises a first toothing arrangement (50) which is in contact with a second toothing arrangement (46) which is arranged on a sidewall (27) of the circumferential groove (24).
  2. Passage wall section (14) according to Claim 1,
    in which the guide ring (26) is in pretensioned contact with the second toothing arrangement (46) by means of a spring element (54) or a plurality of spring elements.
  3. Passage wall section (14) according to Claim 1 or 2,
    in which the guide ring (26) has an outwardly oriented generated surface with at least one external toothing arrangement (35) in which engages toothed wheels (38) which are distributed over the circumference of the passage wall section (14) and are rotatably mounted in this,
    wherein provision is made for an adjusting ring (42) which encompasses all the toothed wheels (38), and at least one internal toothing arrangement (44) of which is in engagement with the toothed wheels (38).
  4. Passage wall section (14) according to Claim 3,
    in which the adjusting ring (42) is rotatable in the circumferential direction via hydraulically or electrically operated push rods.
  5. Passage wall section (14) according to Claim 3 or 4,
    in which provision is made for at least two of the guide rings (26) in question, which are commonly rotatable in the circumferential direction via the one adjusting ring (42).
  6. Passage wall section (14) according to one of the preceding claims,
    in which the guide ring (26) has an abrasive coating (56) or a honeycomb-like coating on its inwardly oriented wall surface (28).
  7. Passage wall section (14) according to one of Claims 3 to 6,
    which for each toothed wheel (38) has a socket (34) arranged on the outer side, in which a shaft or a hub (40) of the toothed wheel (38) is supported.
  8. Passage wall section (14) according to one of the preceding claims,
    in which the guide ring (26) comprises at least two guide ring segments.
  9. Passage wall section (14) according to one of the preceding claims,
    which comprises at least two wall section segments.
  10. Passage wall section (14) according to one of Claims 3 to 9,
    in which the adjusting ring (42) comprises at least two adjusting ring segments.
  11. Axial compressor with a passage wall section (14) according to one of Claims 1 to 10.
  12. Gas turbine with an axial compressor according to Claim 11.
EP10005053A 2010-05-12 2010-05-12 Channel wall section for a ring-shaped flow channel of an axial turbomaschine with blade tip gap adjustment, corresponding axial compressor and gas turbine Not-in-force EP2386726B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP10005053A EP2386726B1 (en) 2010-05-12 2010-05-12 Channel wall section for a ring-shaped flow channel of an axial turbomaschine with blade tip gap adjustment, corresponding axial compressor and gas turbine
US13/104,186 US8721270B2 (en) 2010-05-12 2011-05-10 Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment
JP2011106143A JP5844068B2 (en) 2010-05-12 2011-05-11 Channel wall with adjustable radial clearance for annular channel of axial turbomachinery
CN201110122307.5A CN102242644B (en) 2010-05-12 2011-05-12 Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10005053A EP2386726B1 (en) 2010-05-12 2010-05-12 Channel wall section for a ring-shaped flow channel of an axial turbomaschine with blade tip gap adjustment, corresponding axial compressor and gas turbine

Publications (2)

Publication Number Publication Date
EP2386726A1 EP2386726A1 (en) 2011-11-16
EP2386726B1 true EP2386726B1 (en) 2012-10-31

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US (1) US8721270B2 (en)
EP (1) EP2386726B1 (en)
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DE112015006776T5 (en) * 2015-10-27 2018-05-03 Mitsubishi Heavy Industries, Ltd. rotary engine
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CN112352090B (en) 2018-07-13 2023-01-10 三菱重工业株式会社 Guide plate, steam turbine, inner member, and method for manufacturing guide plate
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CN113107855B (en) * 2021-04-25 2022-12-30 济宁安泰矿山设备制造有限公司 Radial clearance adjusting structure and method and emergency drainage pump

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CN102242644A (en) 2011-11-16
US20110280712A1 (en) 2011-11-17
EP2386726A1 (en) 2011-11-16
CN102242644B (en) 2015-07-22
JP2011236911A (en) 2011-11-24
US8721270B2 (en) 2014-05-13
JP5844068B2 (en) 2016-01-13

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